11results about "Airbags" patented technology

An unmanned cargo loading and transport system adapted for operation with an unmanned aerial vehicle (UAV) comprising a payload pad comprising a plurality of support members movable from an extended mode to a retracted mode when exposed to a lateral force applied to the support members and a payload container adapted to attach to a UAV and pick up cargo from the payload pad by transferring the weight of the cargo from the payload pad to the payload container. The lower portion of the payload container comprises two generally opposed cargo doors movably mounted at opposed sides and movable inwardly to a closed position and outwardly to an open position to receive cargo when the payload container is positioned at the payload pad. The system further comprises a motive power mechanism coupled to the cargo doors for selectively moving the doors between their open and their closed positions.

The invention discloses a household intelligent, light, safe and folding type small manned aircraft which comprises a ground walking system, a rotor wing flight system, a cabin, a fixed wing flight system and the like, and the ground walking system comprises tire supporting legs, stress spring sensors and driving motors; the rotor wing flight system comprises a foldable machine arm, a motor, a rotor wing and an anti-collision radar; the fixed wing flight system comprises a foldable fixed wing, a motor and a rotor wing. The aircraft top adopts the inflatable low-cost parachute, the aircraft bottom adopts the anti-falling safety airbag, the wings are provided with the anti-collision radars, and the micro laser ranging radar is arranged in front, so that the aircraft is safe and reliable to use. The structural part is made of the carbon fiber material, so that the weight is light. The foldable electric vehicle has the advantages of being reasonable in structure, high in practicability, small in size, light in weight, foldable, high in controllability, low in cost, safe, reliable and high in intelligent degree.

The present application relates to an aerial maneuvering apparatus, a control method thereof, and a computer-readable storage medium. An aerial maneuvering apparatus includes a seat in which a safety airbag and a parachute are stored, and an escape portion configured to support the seat mounted to the escape portion, coupled to the aerial maneuvering apparatus to form a part of the aerial maneuvering apparatus, and configured to enable a passenger to perform an emergency jump with the seat to the outside of the aerial maneuvering apparatus when the escape portion is separated from the aerial maneuvering apparatus.

Provided is a reusable airbag inflator including a gas cartridge mounted with an opening or closing valve capable of being opened or closed to discharge a compression gas stored therein, a driving portion for opening or closing the opening or closing valve, and an opening or closing body including a first coupling hole where the opening or closing valve is installed, a second coupling hole where the driving portion is installed, a discharge hole through which the compression gas is discharged to an airbag, and a body cavity connecting the first coupling hole, the second coupling hole, and the discharge hole, wherein the opening or closing valve is a check valve that is opened when external force greater than internal pressure of the gas cartridge is received and closed when the external force is removed.

An aircraft may comprise ducted fans. The ducted fans may be an array of ducted fans. An array of ducted fans may be integrated in a wing of the aircraft. A ducted fan may be integrated in a horizontal tail of the aircraft. The wing may include a movable edge, such as a flap, to provide both exhaust area and flow turning control. The movable edge may be articulated by pivoting the movable edge. The movable edge may be extended and retracted.

An aircraft may include a ducted fan. The ducted fan may be an array of ducted fans. An array of ducted fans may be integrated in a wing of an aircraft. The ducted fan may be integrated in a horizontal tail of an aircraft. The wing may include a movable edge, such as a flap, to provide both an exhaust area and flow steering control. The movable edge may be hinged by pivoting the movable edge. The movable edge may extend and retract.

The invention provides a cold air type gas generator and a using method thereof, and belongs to the technical field of gas generators, the cold air type gas generator comprises a gas cylinder and a trigger device, the trigger device is fixed at a gas outlet of the gas cylinder, the trigger device comprises a shell, a valve needle is slidably connected in the shell, a first vent hole is formed in one end of the shell, and a second vent hole is formed in the other end of the shell; a spring is fixedly connected between the valve needle and the ignition seat, and the end part of the valve needle is arranged close to the first vent hole. The gas cylinder can be inflated again after the cold air type gas generator releases gas, the gas cylinder does not need to be replaced, repeated use of the gas cylinder is achieved, and the single-time use cost of the cold air type gas generator is reduced.

A high-pressure gas tank includes: a tank body including a body portion and a dome portion disposed on one side of the body portion in the axial direction; a cap having a shaft portion extending from a central portion of the dome portion along the axial direction and a through-hole through which the gas flows through the shaft portion; and a protective member that includes a protective portion covering the dome portion around the cap and made of resin and a connecting portion integrated with the protective portion, having an annular shape or a tubular shape into which the shaft portion of the cap is inserted, and made of metal. The cap includes a first threaded portion on an outer periphery of the shaft portion, and the protective member includes a second threaded portion screwed to the first threaded portion on an inner periphery of the connecting portion.

A retractable cargo hook for aircraft is described. The cargo hook comprises a torsion spring allowing rotatable attachment to an aircraft body. An optional recessed portion of the aircraft body can house and receive the cargo hook. This can protect interior components from crashes which can push the cargo hook into the aircraft fuselage, damaging components or even causing post-crash fires.

The present invention provides a safety device capable of controlling a landing point when a flying body falls. The safety device is a safety device provided for a flying body, wherein a first parachute attenuates a falling speed and controls a posture when the flying body falls, a second parachute is opened later than the first parachute and reduces an impact when the flying body lands, a sensor section senses the falling of the flying body, and a control section controls the opening of the first parachute and the second parachute. Furthermore, the control section opens the first parachute at a first timing after the sensor section senses the falling, and opens the second parachute at a second timing after the first timing and further satisfying a prescribed condition.

The disclosure relates to a transitional aircraft. Specifically, the disclosure relates to a transitional aerial vehicle (AV), having a closed polygonal wing member allowing for, inter-alia; smaller dimensions (footprint) compared to AV with same lift / wing surface, higher payload capacity, vertical take-off and landing (VTOL), versatile flight modes (e.g., VTOL, hover, fixed wing cruising, side-to-side flight), effective work with rotors mounted with fixed longitudinal and transverse angle deflection in two arrays, longer flight time and distance, and the ability to self-stabilize landing on and taking off from uneven surfaces, with methods and modular systems for selectably releasing and protecting incorporated payload controllably inflated air-bags.